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Calculation of quasisynchronous orbits of a spacecraft around Phobos for solving the problem of landing on its surface

Cosmic Research volume 46, pages 506–516 (2008)Cite this article

Abstract

The problem of selecting quasi-synchronous orbits of a spacecraft around Phobos is considered. These quasi-synchronous orbits are far (with respect to the Hill’s sphere) quasi-satellite orbits with retrograde rotation in the restricted three body problem. The orbit should pass through a given point at a specified time instant. It should also possess a property of minimum distance from the Phobos surface at every passage above the region of planned landing. The equations of dynamics are represented in the form describing the orbit as a combination of motions in two drifting ellipses, inner and outer ellipses. The center of the outer ellipse is located on the inner ellipse. A formula is derived that relates averaged values of half-axes of the inner and outer ellipses. It is used for construction of the first approximation of numerically designed orbit, which makes it possible to simplify and speed up the computing process. The tables of initial conditions obtained as a result of calculations are presented.

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Authors and Affiliations

  1. Keldysh Institute of Applied Mathematics, Russian Academy of Sciences, Miusskaya pl. 4, Moscow, 125047, Russia

    A. G. Tuchin

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  1. A. G. Tuchin
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Original Russian Text © A.G. Tuchin, 2008, published in Kosmicheskie Issledovaniya, 2008, vol.46, No. 6, pp. 537–547.

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Tuchin, A.G. Calculation of quasisynchronous orbits of a spacecraft around Phobos for solving the problem of landing on its surface. Cosmic Res 46, 506–516 (2008). https://doi.org/10.1134/S0010952508060051

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  • DOI: https://doi.org/10.1134/S0010952508060051

PACS

  • 95.10.Ce